CN111594328B - High-altitude power compensation adjustment control method of aviation hybrid power system - Google Patents
High-altitude power compensation adjustment control method of aviation hybrid power system Download PDFInfo
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- CN111594328B CN111594328B CN202010440518.2A CN202010440518A CN111594328B CN 111594328 B CN111594328 B CN 111594328B CN 202010440518 A CN202010440518 A CN 202010440518A CN 111594328 B CN111594328 B CN 111594328B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02D—CONTROLLING COMBUSTION ENGINES
- F02D41/00—Electrical control of supply of combustible mixture or its constituents
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Abstract
The invention relates to the technical field of high altitude power compensation of an aviation hybrid power system, and particularly discloses a high altitude power compensation regulation control method of the aviation hybrid power system, which comprises the following steps: the method comprises the steps of measuring and calculating the intake oxygen concentration of the hybrid power system according to atmospheric pressure and ambient temperature, adjusting the fuel supply amount of a carburetor according to the real-time oxygen concentration condition, realizing real-time online variable adjustment of air-fuel ratio, and enabling the aviation hybrid power system to work in an optimal efficiency mode when the air-fuel ratio is low; when the aeronautic hybrid power system is in high altitude, the power output of the aeronautic hybrid power system is compensated, so that the aeronautic hybrid power system works in an optimal power area. On one hand, the fuel economy of the aviation hybrid power system is improved, so that the endurance time is improved; on the other hand, the power output is compensated, and the allowable flight height of the unmanned aerial vehicle is increased.
Description
Technical Field
The invention relates to the technical field of high-altitude power compensation of an aviation hybrid power system, and is also suitable for high-altitude power compensation of an aviation piston engine.
Background
The microminiature aviation hybrid power system is a power system solution commonly used by the current industrial unmanned aerial vehicle due to long endurance time and strong load carrying capacity. The core components of the microminiature aviation hybrid power system for the industrial unmanned aerial vehicle are a high-speed two-stroke small-displacement piston engine and a high-speed permanent magnet synchronous motor, the engine drives the motor to generate electricity, and the output electric energy is used by the unmanned aerial vehicle. The flying height of the unmanned aerial vehicle is affected by regions, the altitude is 0 m-4000 m, the atmospheric pressure and the oxygen concentration are obviously reduced along with the rise of the altitude, and therefore the working environment of the aviation hybrid power for the unmanned aerial vehicle is variable.
The aviation hybrid power system is compact in structure, a carburetor with a simple structure is generally used for adjusting the air-fuel ratio of an engine end of the aviation hybrid power system, but the carburetor mechanism with the compact structure does not have the function of automatically adjusting the fuel supply amount, the breathable air amount of the aviation hybrid power system is gradually reduced along with the rise of the flying height, at the moment, the oil supply of the carburetor is not correspondingly adjusted, the output power of the hybrid power system is reduced, the maneuvering performance of the unmanned aerial vehicle is further influenced, even the engine is flameout at high altitude, and safety accidents are caused. On the other hand, the fuel supply is not adjustable, which inevitably leads to a reduction in fuel economy.
Disclosure of Invention
The invention aims to provide a high altitude power compensation adjustment control method of an aviation hybrid power system, which increases the fuel economy of the aviation hybrid power system on one hand, thereby improving the endurance time; on the other hand, the power output is compensated, and the allowable flight height of the unmanned aerial vehicle is increased.
The invention aims to realize a high altitude power compensation adjustment control method of an aviation hybrid power system by the following technical scheme, which is characterized in that the control method is realized by a carburetor oil quantity adjusting device, the carburetor oil quantity adjusting device comprises a steering engine (3), an oil quantity supply screw (8) is arranged on a carburetor (9), and the steering engine (3) is connected with the oil quantity supply screw (8) through a transmission mechanism;
the high-altitude power compensation adjustment control method comprises the following steps:
(1) acquiring three-dimensional map data of atmospheric pressure P, intake air temperature T and intake air oxygen concentration C;
acquiring two-dimensional map data of intake oxygen concentration C and steering engine adjusting signal duty ratio D;
(2) obtaining atmospheric pressure P in real timeFruit of Chinese wolfberryWith inlet air temperature TFruit of Chinese wolfberryInquiring P by using three-dimensional map data of atmospheric pressure P, intake air temperature T and intake air oxygen concentration CFruit of Chinese wolfberryAnd TFruit of Chinese wolfberryCorresponding intake oxygen concentration data CFruit of Chinese wolfberry；
(3) Comparison CFruit of Chinese wolfberryNumerical value with the intake oxygen concentration preset value P _ set:
(3-1) if CFruit of Chinese wolfberryThe method comprises the steps that P _ set is larger than or equal to P _ set, the fact that the aviation hybrid power system works under the oxygen-enriched condition is judged, and the aviation hybrid power system enters the optimal efficiency working mode;
inquiring the two-dimensional map data of the air inlet oxygen concentration C and the steering engine adjusting signal duty ratio D under the optimal efficiency working mode according to the air inlet oxygen concentration C and the steering engine adjusting signal duty ratio DFruit of Chinese wolfberryDuty ratio D of corresponding steering engine adjusting signalFruit of Chinese wolfberryAdjusting duty ratio D of signal by steering engineExample 1Output to the steering engine (3), and the steering engine (3) outputs a signal DFruit of Chinese wolfberryPulse width of (2), reverse rotation, driven by a transmission mechanismThe oil quantity of the oil device (9) is supplied to the adjusting screw (8), so that the oil supply quantity is reduced;
(3-2) if CFruit of Chinese wolfberry<P _ set, judging that the aviation hybrid power system works in the high-altitude oxygen deficiency condition, and enabling the aviation hybrid power system to enter an optimal power working mode;
inquiring the duty ratio D of the steering engine adjusting signal corresponding to the intake oxygen concentration C under the optimal power working mode by using the two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio DExample 2Duty ratio D of steering engine adjusting signalExample 2Output to a steering engine (3), and the steering engine (3) outputs the duty ratio DExample 2The pulse width of the signal is positive rotation, and the oil supply adjusting screw (8) of the carburetor (9) is driven through a transmission mechanism, so that the oil supply is increased;
(4) and (4) repeatedly executing the steps (1) to (3).
Preferably, the transmission mechanism is of a rocker arm connecting rod structure and comprises a steering engine rocker arm (4) and a connecting rod (5), an output shaft of the steering engine (3) is connected with an oil supply screw (8) of the carburetor through the steering engine rocker arm (4) and the connecting rod (5), the steering engine output shaft (3) is fixedly connected with the steering engine rocker arm (4), the steering engine rocker arm (4) is rotatably connected with the connecting rod (5), and the connecting rod (5) is rotatably connected with the oil supply screw (8).
Preferably, the carburetor oil quantity adjusting device further comprises a controller, an atmospheric pressure sensor and an intake air temperature sensor; an atmospheric pressure sensor for acquiring atmospheric pressure P in real timeFruit of Chinese wolfberry；
An inlet air temperature sensor for acquiring the inlet air temperature T in real timeFruit of Chinese wolfberry；
The controller is respectively communicated with the atmospheric pressure sensor, the air inlet temperature sensor and the steering engine;
the controller stores the following information: (1) three-dimensional map data of atmospheric pressure P, intake air temperature T and intake air oxygen concentration C; (2) two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio D;
the controller is used for inquiring PFruit of Chinese wolfberryAnd TFruit of Chinese wolfberryCorresponding intake oxygen concentration data CFruit of Chinese wolfberryAnd comparing CFruit of Chinese wolfberryWith a preset value of intake oxygen concentrationThe numerical size of P _ set;
the controller is also used for inquiring the oxygen concentration C of the inlet airFruit of Chinese wolfberryCorresponding steering engine adjusting signal duty ratio DExample 1、DExample 2And D isExample 1、DExample 2And the control signal is sent to a steering engine to further control the forward and reverse rotation of the steering engine.
Preferably, the atmospheric pressure sensor is arranged on the unmanned aerial vehicle frame.
Preferably, the intake air temperature sensor is disposed in an engine intake duct.
Compared with the prior art, the invention has the advantages that:
the invention comprises an atmospheric pressure sensor, an air inlet temperature sensor, a controller, a steering engine, a rocker arm connecting rod mechanism and a carburetor oil supply adjusting screw, wherein the rocker arm connecting rod mechanism comprises a steering engine rocker arm, a connecting rod, a bearing and a bearing screw. The controller measures and calculates the intake oxygen concentration of the aviation hybrid power system according to the atmospheric pressure sensor and the intake temperature sensor, and decides the working mode of the aviation hybrid power system according to the oxygen concentration value, and the high altitude power compensation adjusting device adjusts the intake air-fuel ratio of the engine in the hybrid system by adjusting the oil supply adjusting screw of the carburetor according to the adjusting algorithm in the corresponding working mode, so as to realize the functions of power compensation or efficiency improvement.
Secondly, according to the operating environment of the unmanned aerial vehicle, a fuel supply system at the engine end of the aviation hybrid power system is continuously adjustable, so that the fine regulation and control of the aviation hybrid system can be realized on the basis; the invention compensates the power loss of the aviation hybrid power system in the high-altitude state and promotes the allowable flight height of the unmanned aerial vehicle; the invention adjusts the efficiency of the aviation hybrid power system in the low-altitude state, improves the fuel economy of the system and further improves the cruising ability of the unmanned aerial vehicle.
Drawings
FIG. 1 is a block diagram of an aero hybrid system of the present invention;
FIG. 2 is a block diagram of the high altitude power compensation apparatus of the present invention;
FIG. 3 is a control schematic of the present invention;
FIG. 4 is a control algorithm diagram of the present invention;
in the figure: the device comprises a 1-aviation hybrid power system, a 2-high altitude power compensation adjusting device, a 3-steering engine, a 4-steering engine rocker arm, a 5-connecting rod, a 6-bearing, a 7-bearing screw, an 8-oil supply adjusting screw and a 9-carburetor.
Detailed Description
The present invention will be further illustrated with reference to the following specific embodiments.
It is to be understood that these embodiments are merely illustrative of the present invention and are not intended to limit the scope of the invention, which is defined in the appended claims, and that modifications in various equivalent forms of the present invention will occur to those skilled in the art upon reading the present invention.
As shown in fig. 1-2, the carburetor oil quantity adjusting device comprises a steering engine (3), an oil quantity supply screw (8) is arranged on a carburetor (9), and the steering engine (3) is connected with the oil quantity supply screw (8) through a transmission mechanism.
The transmission mechanism can be of a rocker arm connecting rod structure and comprises a steering engine rocker arm (4) and a connecting rod (5), an output shaft of the steering engine (3) is connected with an oil supply screw (8) of the carburetor through the steering engine rocker arm (4) and the connecting rod (5), the steering engine output shaft (3) is fixedly connected with the steering engine rocker arm (4), the steering engine rocker arm (4) is rotatably connected with the connecting rod (5), and the connecting rod (5) is rotatably connected with the oil supply screw (8). The transmission mechanism may have other existing configurations.
The carburetor oil quantity adjusting device also comprises a controller, an atmospheric pressure sensor and an air inlet temperature sensor.
The atmospheric pressure sensor is arranged on the unmanned aerial vehicle frame and used for acquiring atmospheric pressure P of a real-time stateFruit of Chinese wolfberry。
An inlet air temperature sensor arranged in the inlet air passage of the engine and used for acquiring the inlet air temperature T in a real-time stateFruit of Chinese wolfberry。
The controller is respectively communicated with the atmospheric pressure sensor, the air inlet temperature sensor and the steering engine. The controller may employ a STM32F1 series of chips.
Firstly, calibrating relevant map data of the aviation hybrid power system by a test method, wherein the method comprises the following steps: three-dimensional map data of atmospheric pressure P, air inlet temperature T and air inlet oxygen concentration C, and two-dimensional map data of air inlet oxygen concentration C and steering engine adjusting signal duty ratio D.
On an aviation hybrid power system test bed, the specific calibration process of three-dimensional map data of atmospheric pressure P, intake temperature T and intake oxygen concentration C is as follows:
1) changing the atmospheric pressure and the air inlet temperature so as to enable the atmospheric pressure sensor to obtain an atmospheric pressure value P and enable the air inlet temperature sensor to obtain an air inlet temperature value T;
2) the intake oxygen concentration value C was measured, thereby obtaining a set of P, T, C data, wherein: c ═ mOxygen gas/mIntake air；
3) And (3) repeating the steps 1) and 2) so as to obtain all P, T, C data covering the whole working environment range of the power system, and forming three-dimensional map data of the atmospheric pressure P, the intake air temperature T and the intake air oxygen concentration C. The three exist in the form of data table (map is data table). The data table is obtained by tests, and the experimental method is called as calibration and is commonly used in the industry.
On an aviation hybrid power system test bed, the specific calibration process of the two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio D is as follows:
1) classifying the measured oxygen concentration C value, and when C is more than or equal to P _ set, carrying out efficiency calibration of duty ratio, otherwise, carrying out power calibration of duty ratio; p _ set is preferably 0.18 to 0.25;
2) in an efficiency calibration mode, adjusting the duty ratio of a steering engine adjusting signal for each corresponding C value to enable the aviation hybrid power system to work in the optimal efficiency state to obtain the optimal D value, and thus obtaining a group of C, D data;
3) in a power calibration mode, adjusting the duty ratio of a steering engine adjusting signal for each corresponding C value to enable the aviation hybrid power system to work in a maximum power state to obtain an optimal D value, and thus obtaining a group of C, D data;
4) and (3) repeating the steps 2) and 3) so as to obtain D values corresponding to all the C values, and thus obtaining two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio D. Both exist in the form of data tables, (map is a data table). The data table is obtained by tests, and the experimental method is called as calibration and is commonly used in the industry.
As shown in fig. 3-4, a high altitude power compensation adjustment control method for an aviation hybrid power system includes the following steps:
(1) the atmospheric pressure sensor and the air inlet temperature sensor input the current atmospheric pressure value and the air inlet temperature value into the controller, three-dimensional map data of the atmospheric pressure P, the air inlet temperature T and the air inlet oxygen concentration C are stored in the controller, and the controller inquires the air inlet oxygen concentration data C corresponding to the atmospheric pressure P and the air inlet temperature TFruit of Chinese wolfberry；
(2) The controller compares the oxygen concentration C of the inlet airFruit of Chinese wolfberryThe value of P _ set is compared with the preset value, if CFruit of Chinese wolfberryThe controller judges that the aviation hybrid power system works under the oxygen-enriched condition and enters an optimal efficiency working mode; if CFruit of Chinese wolfberry<P _ set, the controller judges that the aviation hybrid power system works under the high-altitude oxygen deficiency condition, and the controller enters an optimal power working mode;
(3) and controlling two-dimensional map data in which the intake oxygen concentration C and the steering engine adjusting signal duty ratio D are stored. In the optimum efficiency mode, the controller queries the mode and the intake oxygen concentration CFruit of Chinese wolfberryDuty ratio D of corresponding steering engine adjusting signalExample 1The signal is output to a steering engine 3, the steering engine 3 reversely rotates according to the pulse width of the signal to drive a steering engine rocker arm 4 and a connecting rod mechanism connected with the steering engine rocker arm to finally drive the oil quantity of a carburetor to supply an adjusting screw 8, so that the oil supply quantity is reduced, the air-fuel ratio of an engine of an aviation hybrid power system is in an economic gas mixture range, and the oil consumption of the hybrid power system is reduced;
in the optimum power mode of operation, the controller queries the mode and the intake oxygen concentration CFruit of Chinese wolfberryDuty ratio D of corresponding steering engine adjusting signalExample 2The signal is output to a steering engine 3, the steering engine 3 drives a steering engine rocker arm 4 and a connecting rod mechanism connected with the steering engine rocker arm according to the pulse width of the signal in the forward direction to finally drive the oil supply of a carburetor to an adjusting screw 8, so that the oil supply is increased, the air-fuel ratio of an engine of an aviation hybrid power system is in a power mixed gas range, and mixed gas is compensatedPower loss of the force system;
(4) and after the system is delayed for a certain time, the operation is continuously repeated so as to continuously correct the fuel efficiency and the power output of the aviation hybrid power system.
P _ set is preferably 0.18-0.25.
The method comprises the following steps of (1) measuring and calculating the intake oxygen concentration of the aviation hybrid power system in real time: the real-time measurement and calculation of the oxygen concentration is a basic condition for realizing the functions, and an air inlet temperature sensor is arranged in an air inlet channel of an engine in an aviation hybrid power system and used for measuring the air inlet temperature; an atmospheric pressure sensor is arranged on the unmanned aerial vehicle frame and used for measuring atmospheric pressure. The controller stores data map of atmospheric pressure, temperature and intake oxygen concentration, and after the sensor collects data and inputs the data into the controller, the controller searches the map to obtain real-time intake oxygen concentration data according to the collected atmospheric pressure value and intake air temperature. And the working mode of the hybrid system and the corresponding oil quantity demand are calculated according to the intake oxygen concentration data. And the data map is obtained by system calibration.
Selecting the working mode of the aviation hybrid power system: when the concentration of intake oxygen is higher than a set threshold P _ set, the controller judges that the aviation hybrid power system is in a low-altitude oxygen-enriched environment, the hybrid system enters an optimal efficiency working mode at the moment, the fuel supply of the carburetor is adjusted according to the optimal efficiency mode, the fuel supply is reduced, the air-fuel ratio of the engine is increased, and the air-fuel ratio of the engine is in an economic mixture range; when the concentration of the intake oxygen is lower than a set threshold value P _ set, the controller judges that the aviation hybrid power system is in a high altitude oxygen-deficient environment, the hybrid system enters an optimal power working mode at the moment, the fuel supply of the carburetor is adjusted according to the optimal power mode, the fuel supply is increased, the air-fuel ratio of the engine is reduced, and the air-fuel ratio of the engine is in a power mixed gas range.
Aviation hybrid power system oil mass supply adjustment mechanism: the oil supply adjusting mechanism comprises a steering engine and a rocker arm connecting rod mechanism, and the rocker arm connecting rod mechanism comprises a steering engine rocker arm, a connecting rod and a carburetor oil quantity adjusting rocker arm. The controller stores data map of the intake oxygen concentration and the steering engine pulse width duty ratio, and can obtain the duty ratio of the pulse width signal required by the steering engine in real time according to the intake oxygen concentration. If the hybrid power system works in the optimal efficiency mode, duty ratio data acquired by the controller reversely controls the steering engine to rotate, and the oil supply screw of the carburetor is adjusted through the rocker arm connecting rod mechanism, so that the oil supply is correspondingly reduced, and the air-fuel ratio of the engine tends to an economic air-fuel mixture range (air-fuel mixture when the air excess coefficient of the air intake of the engine is 1.05-1.15). If the hybrid power system works in the optimal power mode, the duty ratio data acquired by the controller positively controls the steering engine to rotate, the oil supply screw of the carburetor is adjusted through the rocker arm connecting rod mechanism, the oil supply is correspondingly increased, the air-fuel ratio of the engine tends to the power mixed gas range (power mixed gas, the excess air coefficient is 0.85-0.95), and high-altitude power compensation is performed on the aviation hybrid power system.
The invention can measure and calculate the intake oxygen concentration of the hybrid power system according to atmospheric pressure and ambient temperature, and adjust the fuel supply quantity of the carburetor according to the real-time oxygen concentration condition, realize the real-time online variable regulation of the air-fuel ratio, make the aviation hybrid power system work in the optimum efficiency mode when the low-altitude; when the aeronautic hybrid power system is in high altitude, the power output of the aeronautic hybrid power system is compensated, so that the aeronautic hybrid power system works in an optimal power area.
Claims (5)
1. A high altitude power compensation adjustment control method of an aviation hybrid power system is characterized in that the control method is realized through a carburetor oil quantity adjusting device, the carburetor oil quantity adjusting device comprises a steering engine (3), an oil quantity supply screw (8) is arranged on a carburetor (9), and the steering engine (3) is connected with the oil quantity supply screw (8) through a transmission mechanism;
the high-altitude power compensation adjustment control method comprises the following steps:
(1) acquiring three-dimensional map data of atmospheric pressure P, intake air temperature T and intake air oxygen concentration C;
acquiring two-dimensional map data of intake oxygen concentration C and steering engine adjusting signal duty ratio D;
(2) obtaining atmospheric pressure P in real timeFruit of Chinese wolfberryWith inlet air temperature TFruit of Chinese wolfberryUsing atmospheric pressure P, intake airTemperature T and intake oxygen concentration C three-dimensional map data, query PFruit of Chinese wolfberryAnd TFruit of Chinese wolfberryCorresponding intake oxygen concentration data CFruit of Chinese wolfberry；
(3) Comparison CFruit of Chinese wolfberryNumerical value with the intake oxygen concentration preset value P _ set:
(3-1) if CFruit of Chinese wolfberryThe method comprises the steps that P _ set is larger than or equal to P _ set, the fact that the aviation hybrid power system works under the oxygen-enriched condition is judged, and the aviation hybrid power system enters the optimal efficiency working mode; the best efficiency working mode is as follows: the air-fuel ratio of an engine of the aviation hybrid power system tends to an economic air-fuel mixture range, and the air-fuel mixture is the air-fuel mixture when the air-fuel ratio of the air-fuel mixture of the engine is 1.05-1.15;
inquiring the two-dimensional map data of the air inlet oxygen concentration C and the steering engine adjusting signal duty ratio D under the optimal efficiency working mode according to the air inlet oxygen concentration C and the steering engine adjusting signal duty ratio DFruit of Chinese wolfberryDuty ratio D of corresponding steering engine adjusting signalExample 1Adjusting duty ratio D of signal by steering engineExample 1Output to the steering engine (3), and the steering engine (3) outputs a signal DExample 1The pulse width of the oil supply valve is in reverse rotation, and an oil supply adjusting screw (8) of a carburetor (9) is driven through a transmission mechanism, so that the oil supply amount is reduced;
(3-2) if CFruit of Chinese wolfberry<P _ set, judging that the aviation hybrid power system works in the high-altitude oxygen deficiency condition, and enabling the aviation hybrid power system to enter an optimal power working mode; the optimal power operation mode is as follows: the air-fuel ratio of the engine of the aviation hybrid power system is in a power air-fuel mixture range, and the excess air coefficient is 0.85-0.95;
inquiring the duty ratio D of the steering engine adjusting signal corresponding to the intake oxygen concentration C under the optimal power working mode by using the two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio DExample 2Duty ratio D of steering engine adjusting signalExample 2Output to a steering engine (3), and the steering engine (3) outputs the duty ratio DExample 2The pulse width of the signal is positive rotation, and the oil supply adjusting screw (8) of the carburetor (9) is driven through a transmission mechanism, so that the oil supply is increased;
(4) and (4) repeatedly executing the steps (1) to (3).
2. The high altitude power compensation adjustment control method of the aviation hybrid power system according to claim 1, characterized in that the transmission mechanism is a rocker arm and connecting rod structure, and comprises a steering engine rocker arm (4) and a connecting rod (5), wherein an output shaft of the steering engine (3) is connected with an oil supply screw (8) of a carburetor through the steering engine rocker arm (4) and the connecting rod (5), the output shaft of the steering engine (3) is fixedly connected with the steering engine rocker arm (4), the steering engine rocker arm (4) is rotatably connected with the connecting rod (5), and the connecting rod (5) is rotatably connected with the oil supply screw (8).
3. The high altitude power compensation adjustment control method of an aviation hybrid power system as claimed in claim 1,
the carburetor oil quantity adjusting device also comprises a controller, an atmospheric pressure sensor and an air inlet temperature sensor;
an atmospheric pressure sensor for acquiring atmospheric pressure P in real timeFruit of Chinese wolfberry；
An inlet air temperature sensor for acquiring the inlet air temperature T in real timeFruit of Chinese wolfberry；
The controller is respectively communicated with the atmospheric pressure sensor, the air inlet temperature sensor and the steering engine;
the controller stores the following information: (1) three-dimensional map data of atmospheric pressure P, intake air temperature T and intake air oxygen concentration C; (2) two-dimensional map data of the intake oxygen concentration C and the steering engine adjusting signal duty ratio D;
the controller is used for inquiring PFruit of Chinese wolfberryAnd TFruit of Chinese wolfberryCorresponding intake oxygen concentration data CFruit of Chinese wolfberryAnd comparing CFruit of Chinese wolfberryThe value of the oxygen concentration of the inlet air is compared with the preset value P _ set;
the controller is also used for inquiring the oxygen concentration C of the inlet airFruit of Chinese wolfberryCorresponding steering engine adjusting signal duty ratio DExample 1、DExample 2And D isExample 1、DExample 2And the control signal is sent to a steering engine to further control the forward and reverse rotation of the steering engine.
4. The high altitude power compensation adjustment control method of an aviation hybrid power system as claimed in claim 3,
the atmospheric pressure sensor is arranged on the unmanned aerial vehicle frame.
5. The high altitude power compensation adjustment control method of an aviation hybrid power system as claimed in claim 3,
the air inlet temperature sensor is arranged in an air inlet channel of the engine.
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| JP2004036541A (en) * | 2002-07-04 | 2004-02-05 | Toyota Motor Corp | Fuel supply control device for internal combustion engine |
| CN102705109A (en) * | 2012-06-18 | 2012-10-03 | 中国南方航空工业(集团)有限公司 | Device for adjusting oil quantity |
| KR20150053829A (en) * | 2013-10-16 | 2015-05-19 | 우진공업주식회사 | Air fuel ratio measuring device having self calibration function and method for controlling the same |
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